Mapping tow splices in composite structures

• US 8,695,669 B2
• Filed: 05/09/2012
• Issued: 04/15/2014
• Est. Priority Date: 07/26/2009
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Engelbart, Roger W., Hannebaum, Reed, Rector, Eric
• Primary Examiner(s): KOCH, GEORGE R
• Application Number:
  US13/467,160
• Publication Number:
  US 20120216957A1
• Time in Patent Office: 706 Days
• Field of Search: 156/351, 156/361, 156/367, 156/378, 156/379, 156/64, 356/237.1, 356/237.3, 356/237.4, 356/238.3
• US Class Current: 156/351
• CPC Class Codes: B29C 70/384 Fiber placement heads, e.g. component parts, details or accessories

Abstract

The three dimensional (3-D) locations of splices in pre-preg tows placed by an automatic fiber placement machine to form a laminated composite structure are mapped to allow visualization of alignment patterns in the splices.

Claims

1. An apparatus configured to detect and identify tow segment end joint alignments through a thickness of a composite structure, the apparatus comprising:

an automatic fiber placement machine comprising a compaction roller configured to compact a tow

a sensing device configured to detect, immediately after the compaction roller compacts the tow on a tool, a splice marking, such that the splice marking is at least one of;

on a surface of the tow, and within the tow;

a geometric database of the composite structure; and

a computer comprising a program code configured to;

receive data from the geometric database, determine a location of the splice marking within the composite structure, receive an inspection parameter, and generate a pass/fail status for the tow segment end joint alignments based upon the inspection parameter.

2. The apparatus of claim 1, further comprising:

an illumination source configured to illuminate the tows as the tows are being placed, and

a sensor configured to detect a presence of each splice marking illuminated by the illumination source.

3. The apparatus of claim 2, wherein the sensing device includes a camera adapted to be mounted on the placement machine and oriented to image an area of the tows immediately after they are placed on the tool.

4. The apparatus of claim 1, wherein the geometric database comprises a three-dimensional data file.

5. The apparatus of claim 4, further comprising a software program used by the computer to generate the three-dimensional data file representing a three-dimensional image of the structure showing the location of the splice marking within the structure.

6. The apparatus of claim 1, such that identify tow segment end joint alignments further comprises:

the program code configured to generate on a display, a map of the composite structure showing the location of each splice marking within the composite structure.

7. The apparatus of claim 6, such that the map is a three-dimensional map displaying the location and alignments of each splice marking through the thickness of the composite structure.

8. The apparatus of claim 1, such that the inspection parameter comprises load bearing capability specifications of the composite structure.

9. The apparatus of claim 1, such that the splice marking comprises a magnetic element, and the sensing device comprises a magnetic sensor.

10. The apparatus of claim 1, such that the sensing device is a high resolution solid state array of cameras.

11. An apparatus configured to map and evaluate a three-dimensional alignment of tow segment end joints in pre-preg tows and to form a laminated composite structure, comprising:

an automatic fiber placement machine comprising a compaction roller configured to compact a tow

at least one sensor configured to sense a splice marking after placing the tow onto a tool;

a computer coupled with the sensor, the computer comprising program code configured to calculate a three-dimensional coordinate within the structure of each splice marking sensed by the sensor, receive an inspection parameter, and determine if the three-dimensional alignment of a first tow segment end joint relative to a second tow segment end joint meets the inspection parameter; and

a display coupled with the computer configured to display an image showing the three-dimensional alignment of each splice marking through a thickness of the laminated composite structure.

12. The apparatus of claim 11, wherein the sensor includes an image recording device.

13. The apparatus of claim 12, further comprising an illumination source configured to illuminate the tows as the tows are being placed onto the tool.

14. The apparatus of claim 13, wherein the inspection parameter depends upon a direction of a load place on the laminated composite structure.

15. The apparatus of claim 13, wherein the image recording device and the illumination source are mounted on the fiber placement machine.

16. The apparatus of claim 11, wherein the tows include a feature at each splice marking, and the sensor senses the feature.

17. The apparatus of claim 16, such that the feature is within the tows.

18. The apparatus of claim 16, such that the feature is magnetic.

19. An apparatus configured to manufacture a laminated composite aircraft structure, comprising:

an automatic fiber placement machine, including a tape application head configured to place bands of pre-preg tows on a tool surface;

at least one camera on the application head and configured to image areas of the band immediately after the pre-preg tows have been placed on the tool surface by a placement head, and the at least one camera further configured to record a three-dimensional location of a feature that is inside the pre-preg tows representing a splice in the tow;

a laser configured to illuminate the area of the band imaged by the camera;

a computer coupled with the camera, the computer configured comprising a program code configured to;

recognize the feature recorded by the camera, generate a three-dimensional data file representing a three-dimensional image of the structure, the three dimensional data file comprising the location of the splice, and a three-dimensional alignment of each splice through a thickness of the laminated composite aircraft structure, and further configured to receive inspection parameters and determine if the three-dimensional alignment of each splice through the thickness of the composite structure meets inspection parameters; and

a display coupled with the computer, the display configured to display the three-dimensional image of the structure including the three-dimensional location of the splice through the thickness of the composite structure.

20. The apparatus of claim 19, such that the inspection parameters comprise load bearing capability specifications of the laminated composite aircraft structure.